CN106670813A - Forming method and mold for airplane clamping hoop part - Google Patents
Forming method and mold for airplane clamping hoop part Download PDFInfo
- Publication number
- CN106670813A CN106670813A CN201611154014.4A CN201611154014A CN106670813A CN 106670813 A CN106670813 A CN 106670813A CN 201611154014 A CN201611154014 A CN 201611154014A CN 106670813 A CN106670813 A CN 106670813A
- Authority
- CN
- China
- Prior art keywords
- clamping plate
- fuse
- plate
- left clamping
- right clamping
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P23/00—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass
- B23P23/04—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass for both machining and other metal-working operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Abstract
The invention discloses a forming method and mold for an airplane clamping hoop part. The forming mold comprises a bottom plate, a core, a right clamping plate and a left clamping plate; the core is fixed to the middle of the bottom plate through a connecting piece; a transverse through hole is formed in a tail handle of the core; the inner side of the right clamping plate and the inner side of the left clamping plate are matched with the outside molded surface of the clamping hoop part; the front end of the right clamping plate and the front end of the left clamping plate are hinged to the front end of the bottom plate through a connecting piece; the right clamping plate, the left clamping plate and the core form a molded surface of the part; the rear end of the right clamping plate and the rear end of the left clamping plate are each provided with a drill bushing hole corresponding to the through hole formed in the tail handle of the core; a strip-shaped plate material is clamped between the core, the right clamping plate and the left clamping plate; and the right clamping plate, the left clamping plate and the core are combined through the handle, and then connection holes in the two ends of the clamping hoop part are manufactured through the coaxial drill bushing holes and the through hole in the tail of the core.
Description
Technical field
The present invention relates to aircraft manufacturing technology, the manufacturing process and shaping dies of specifically a kind of aircraft clip class part.
Background technology
Aircraft clip class part is a kind of curved class part of plate for connecting pipe, due to aircraft pipeline it is many, pipe diameter
Different, so aircraft clip class part specifications are a lot, but batch is little.Two sets of bending dies and a set of drill jig are typically needed during shaping.Two
Set bending die is used to shape the profile of clip class part on punch press, and drill jig is used to drill the hole on part.Using this side
Legal system makes part, needs three molds, and die manufacturing cycle is long, high cost, low production efficiency, it is impossible to meet the need of Aircraft Production
Will.For such case, urgent need will find a kind of new easy manufacturing process to meet the need of aircraft clip class part production
Ask.It is required that mould structure is simple, be easy to manufacture, the manufacturing cycle is short, low cost.Require that mould is easy to use simultaneously, it is easy to operate, with
Improve production efficiency.
The content of the invention
The purpose of the application is to provide a kind of new easy aircraft clip class part shaping techniques and shaping dies.
A kind of aircraft clip class part forming mould, it is characterised in that：The mould contains base plate, fuse, right clamping plate, Zuo Jia
Plate, the main body of described fuse is the block structure of a circle, and the afterbody of fuse has the caudal peduncle of strip and block, its profile and clip
Part medial type face matches, and fuse is fixed on the middle part of base plate by connector, horizontal through hole is provided with the caudal peduncle of fuse, right
The inner side of clamping plate and left clamping plate matches with the lateral face of clip part, and the front end of right clamping plate and left clamping plate is hinged by connector
In the front end of base plate, right clamping plate and left clamping plate and fuse are combined into the rear end point of the forming face of part, right clamping plate and left clamping plate
Drill bushing hole corresponding with fuse caudal peduncle through hole is not provided with, in the rear end tails of right clamping plate and left clamping plate handle is additionally provided with.
When using, the plate of strip is clamped between fuse and right clamping plate and left clamping plate, by handle make right clamping plate and
Left clamping plate and the matched moulds of fuse, shape clip part shape, then are made by the through hole in coaxial drill bushing hole and fuse afterbody
The connecting hole at clip part two ends.
The beneficial effects of the present invention is, forming die structure is rationally simple, easy to use, using one set of die, can
The profile of formation of parts, can drill the hole on part again, fully meet the demand of aircraft clip class part production.
With reference to embodiments accompanying drawing is described in further detail to the application.
Description of the drawings
Fig. 1 is the aircraft clip class part forming mould of the application.
Fig. 2 is that the lateral structure of Fig. 1 is illustrated.
Fig. 3 is the horizontality structural representation of Fig. 1.
Fig. 4 is the aircraft clip class part shaping techniques of the application.
Explanation is numbered in figure：1 fuse, 2 right clamping plates, 3 rank type screws, 4 left clamping plates, 5 base plates, 6 connectors, 7 handles, 8 are bored
Set hole, 9 through holes, 10 clip parts.
Specific embodiment
Referring to accompanying drawing, the aircraft clip class part forming mould of the application, containing base plate 5, fuse 1, right clamping plate 2, Zuo Jia
Plate 4, the main body of described fuse 1 is the block structure of a circle, and the afterbody of fuse has the caudal peduncle of strip and block, outside fuse 1
Shape is matched with the medial type face of clip part 10, and fuse 1 is fixed on the middle part of base plate 5 by connector 6, and the caudal peduncle portion of fuse 1 sets
There is the inner side of horizontal through hole 9, right clamping plate 2 and left clamping plate 4 to match with the lateral face of clip part 10, right clamping plate 2 and left folder
Plate 4 is combined into the front end of the both sides forming face of part, right clamping plate 2 and left clamping plate 4 with fuse 1 and passes through connector rank type screw 3
The rear end for being hinged on the front end of base plate 5, right clamping plate 2 and left clamping plate 4 is respectively equipped with and the corresponding drill bushing hole of fuse caudal peduncle portion through hole 9
8, it is additionally provided with handle 7 in the rear end tails of right clamping plate 2 and left clamping plate 4.
Using method is as follows：It is the plate of a strip before the shaping of aircraft clip class part 10, the plate of strip is clamped in
Between fuse 1 and right clamping plate 2 and left clamping plate 4, operation handle 7 makes right clamping plate 2, left clamping plate 4 rotate around rank type screw 3, closure
Right clamping plate 2 and left clamping plate 4 and the matched moulds of fuse 1, the plate for making strip is adjacent to and pastes contour forming on fuse 1, using instrument by the right side
Make the connecting hole at the two ends of clip part 10 in the coaxial drill bushing hole 8 of clamping plate 2, left clamping plate 4.
Claims (2)
1. a kind of aircraft clip class part shaping techniques, it is characterised in that 1) have a shaping dies, the mould contain base plate,
Fuse, right clamping plate, left clamping plate, the main body of described fuse is the block structure of a circle, and the afterbody of fuse has strip and block
Caudal peduncle, its profile is matched with clip part medial type face, and fuse is fixed on the middle part of base plate by connector, at the caudal peduncle of fuse
It is provided with the inner side of horizontal through hole, right clamping plate and left clamping plate to match with the lateral face of clip part, right clamping plate and left clamping plate
Front end is hinged on the front end of base plate by connector, and right clamping plate and left clamping plate are combined into the forming face of part, right folder with fuse
The rear end of plate and left clamping plate is respectively equipped with drill bushing hole corresponding with fuse caudal peduncle through hole, in right clamping plate and the rear end tails of left clamping plate
It is additionally provided with handle；2) plate of strip is clamped between fuse and right clamping plate and left clamping plate, right clamping plate and a left side is made by handle
The matched moulds of clamping plate and fuse, then the connecting hole for making clip part two ends by the through hole in coaxial drill bushing hole and fuse afterbody is i.e.
Can.
2. a kind of aircraft clip class part forming mould, it is characterised in that：The mould contains base plate, fuse, right clamping plate, Zuo Jia
Plate, the main body of described fuse is the block structure of a circle, and the afterbody of fuse has the caudal peduncle of strip and block, its profile and clip
Part medial type face matches, and fuse is fixed on the middle part of base plate by connector, horizontal through hole is provided with the caudal peduncle of fuse, right
The inner side of clamping plate and left clamping plate matches with the lateral face of clip part, and the front end of right clamping plate and left clamping plate is hinged by connector
In the front end of base plate, right clamping plate and left clamping plate and fuse are combined into the rear end point of the forming face of part, right clamping plate and left clamping plate
Drill bushing hole corresponding with fuse caudal peduncle through hole is not provided with, in the rear end tails of right clamping plate and left clamping plate handle is additionally provided with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611154014.4A CN106670813A (en) | 2016-12-14 | 2016-12-14 | Forming method and mold for airplane clamping hoop part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611154014.4A CN106670813A (en) | 2016-12-14 | 2016-12-14 | Forming method and mold for airplane clamping hoop part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106670813A true CN106670813A (en) | 2017-05-17 |
Family
ID=58869228
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611154014.4A Pending CN106670813A (en) | 2016-12-14 | 2016-12-14 | Forming method and mold for airplane clamping hoop part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106670813A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114888196A (en) * | 2022-05-23 | 2022-08-12 | 成都飞机工业（集团）有限责任公司 | Forming device and forming method for waist-shaped hoop |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202963296U (en) * | 2012-12-11 | 2013-06-05 | 成都飞机工业（集团）有限责任公司 | Manual band clamping piece forming device |
| CN203649143U (en) * | 2013-11-04 | 2014-06-18 | 内蒙古航天红岗机械有限公司 | Fixing ring forming tool |
| CN104139281A (en) * | 2014-06-27 | 2014-11-12 | 湖北三江航天红阳机电有限公司 | Arc-shaped titanium alloy thin-walled part forming tooling and method |
| CN205183404U (en) * | 2015-10-27 | 2016-04-27 | 成都飞机工业（集团）有限责任公司 | Manual bending device of self -adaptation |
| CN206435983U (en) * | 2016-12-14 | 2017-08-25 | 中航飞机股份有限公司西安飞机分公司 | A kind of aircraft clip class part forming mould |
-
2016
- 2016-12-14 CN CN201611154014.4A patent/CN106670813A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202963296U (en) * | 2012-12-11 | 2013-06-05 | 成都飞机工业（集团）有限责任公司 | Manual band clamping piece forming device |
| CN203649143U (en) * | 2013-11-04 | 2014-06-18 | 内蒙古航天红岗机械有限公司 | Fixing ring forming tool |
| CN104139281A (en) * | 2014-06-27 | 2014-11-12 | 湖北三江航天红阳机电有限公司 | Arc-shaped titanium alloy thin-walled part forming tooling and method |
| CN205183404U (en) * | 2015-10-27 | 2016-04-27 | 成都飞机工业（集团）有限责任公司 | Manual bending device of self -adaptation |
| CN206435983U (en) * | 2016-12-14 | 2017-08-25 | 中航飞机股份有限公司西安飞机分公司 | A kind of aircraft clip class part forming mould |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114888196A (en) * | 2022-05-23 | 2022-08-12 | 成都飞机工业（集团）有限责任公司 | Forming device and forming method for waist-shaped hoop |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170517 |
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| WD01 | Invention patent application deemed withdrawn after publication |